Induced rolling moment for NACA4412 plain and flapped wing

Purpose – The paper aims to compute rolling moments on a follower aircraft wing due to vortices generated by a plain and flapped NACA4412 wing using experimental particle image velocimetery (PIV) data. Design/methodology/approach – This paper describes the detailed variation of the induced rolli...

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Main Authors:	Elsayed, Omer Ali, Kwon, Kijung, Asrar, Waqar, Omar, Ashraf Ali E.
Format:	Article
Language:	English
Published:	Emerald Group Publications Limited 2010
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/1969/ http://irep.iium.edu.my/1969/ http://irep.iium.edu.my/1969/ http://irep.iium.edu.my/1969/1/Induced_rolling%5B1%5D.pdf

id	iium-1969
recordtype	eprints
spelling	iium-19692011-11-14T05:27:17Z http://irep.iium.edu.my/1969/ Induced rolling moment for NACA4412 plain and flapped wing Elsayed, Omer Ali Kwon, Kijung Asrar, Waqar Omar, Ashraf Ali E. TL500 Aeronautics Purpose – The paper aims to compute rolling moments on a follower aircraft wing due to vortices generated by a plain and flapped NACA4412 wing using experimental particle image velocimetery (PIV) data. Design/methodology/approach – This paper describes the detailed variation of the induced rolling moment on a follower aircraft wing derived from a PIV velocity field measurement. A rectangular wing of a subsonic wall interference model is used as a vortex generator in two different configurations: plain wing of NACA4412 cross-section profile; and flapped wing with trailing edge flap of NACA0012 cross-section profile extended at 20°. Findings – Results obtained showed that the maximum induced rolling moment coefficient depends on the strength of the vortex produced by the generating aircraft wing and increases linearly with the increment of the angle of attack. Originality/value – This paper provides an insight on the effects of different angles of attacks for plain and flapped wings on the induced rolling moment coefficient and therefore, the hazard imposed on the following aircraft can be estimated. Emerald Group Publications Limited 2010-01 Article PeerReviewed application/pdf en http://irep.iium.edu.my/1969/1/Induced_rolling%5B1%5D.pdf Elsayed, Omer Ali and Kwon, Kijung and Asrar, Waqar and Omar, Ashraf Ali E. (2010) Induced rolling moment for NACA4412 plain and flapped wing. International Journal of Aircraft Engineering and Aerospace Technology, 82 (1). pp. 23-32. ISSN 0002-2667 http://www.emeraldinsight.com/journals.htm?issn=0002-2667&volume=82&issue=1&articleid=1840379&show=abstract 10.1108/00022661011028083
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics Elsayed, Omer Ali Kwon, Kijung Asrar, Waqar Omar, Ashraf Ali E. Induced rolling moment for NACA4412 plain and flapped wing
description	Purpose – The paper aims to compute rolling moments on a follower aircraft wing due to vortices generated by a plain and flapped NACA4412 wing using experimental particle image velocimetery (PIV) data. Design/methodology/approach – This paper describes the detailed variation of the induced rolling moment on a follower aircraft wing derived from a PIV velocity field measurement. A rectangular wing of a subsonic wall interference model is used as a vortex generator in two different configurations: plain wing of NACA4412 cross-section profile; and flapped wing with trailing edge flap of NACA0012 cross-section profile extended at 20°. Findings – Results obtained showed that the maximum induced rolling moment coefficient depends on the strength of the vortex produced by the generating aircraft wing and increases linearly with the increment of the angle of attack. Originality/value – This paper provides an insight on the effects of different angles of attacks for plain and flapped wings on the induced rolling moment coefficient and therefore, the hazard imposed on the following aircraft can be estimated.
format	Article
author	Elsayed, Omer Ali Kwon, Kijung Asrar, Waqar Omar, Ashraf Ali E.
author_facet	Elsayed, Omer Ali Kwon, Kijung Asrar, Waqar Omar, Ashraf Ali E.
author_sort	Elsayed, Omer Ali
title	Induced rolling moment for NACA4412 plain and flapped wing
title_short	Induced rolling moment for NACA4412 plain and flapped wing
title_full	Induced rolling moment for NACA4412 plain and flapped wing
title_fullStr	Induced rolling moment for NACA4412 plain and flapped wing
title_full_unstemmed	Induced rolling moment for NACA4412 plain and flapped wing
title_sort	induced rolling moment for naca4412 plain and flapped wing
publisher	Emerald Group Publications Limited
publishDate	2010
url	http://irep.iium.edu.my/1969/ http://irep.iium.edu.my/1969/ http://irep.iium.edu.my/1969/ http://irep.iium.edu.my/1969/1/Induced_rolling%5B1%5D.pdf
first_indexed	2023-09-18T20:09:31Z
last_indexed	2023-09-18T20:09:31Z
_version_	1777407383414243328

Induced rolling moment for NACA4412 plain and flapped wing

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